Abstract
Aerofoils NACA 2S-(50)(05)-(50)(05) and NACA 2S-(75)(05)-(75)(05), 2D symmetric biconvex circular arc are considered for analysis of supersonic regime. The work is aimed to determine the effect on force characteristics by shifting the location of maximum thickness toward the trailing edge. Fluent (Ansys V 12.0) tool is used for the study with the consideration of unsteady, viscous and laminar compressible flow model at three different angles of attack at α = 0°, 10°, 20° in the Mach number range of (1.25–2.13) keeping Reynolds number fixed at 5 × 105. It is found that there is a slight reduction of drag by shifting its location at α = 0° and higher L/D ratio also achieved at higher Mach no. for α = 10° and 20° because of a high intensity shock wave at beneath surface.
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References
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Prasad, R., Agarwal, S., Singh, D., Singh, M. (2021). Comparison of Supersonic Flow Regime for Two Different Symmetric Biconvex Circular-Arc Aerofoil. In: Sikarwar, B.S., Sundén, B., Wang, Q. (eds) Advances in Fluid and Thermal Engineering. Lecture Notes in Mechanical Engineering. Springer, Singapore. https://doi.org/10.1007/978-981-16-0159-0_35
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DOI: https://doi.org/10.1007/978-981-16-0159-0_35
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